Directional control of missiles

ABSTRACT

Missile ( 10 ) includes one or more arrays of barrel assemblies ( 11 ) which are displaced from the centre of gravity of missile ( 10 ). Each barrel assembly ( 11 ) includes a plurality of projectiles axially disposed within a barrel, and each projectile is associated with a discrete propellant charge for propelling the projectile sequentially from the barrel. Each array of barrel assemblies ( 13, 14 ) is capable of selectively firing the projectiles from selected barrels ( 11   a ) whereby missile ( 10 ) is accelerated by the reactionary force generated by said firing of projectiles and the missile is deflected (A) onto a new course or trajectory. This enables missile ( 10 ) to be steered to intercept its target ( 20 ), even if the target is undertaking evasive manoeuvres. Each barrel assembly ( 11 ) can include up to twelve projectiles.

BACKGROUND OF THE INVENTION

[0001] 1. Field of the Invention

[0002] The present invention relates to directional control of missiles.In particular the present invention relates to missiles capable ofdirectional control and to a process of directionally controlling amissile.

[0003] 1. Discussion of the Background Art

[0004] Missiles are objects that can be propelled or shot, towards atarget. Missiles include a variety of objects, many of which will beapplicable to the present invention. For example, missiles such as highaltitude ballistic missiles or out of atmosphere ballistic missiles arewidely employed as long-range strike weapons as they are very effectiveand difficult to detect in time for adequate defences to be actioned.High altitude ballistic missiles may be required to make swiftcorrections to flight paths in order to avoid attack, such as fromdirectionally controlled missiles.

[0005] Directionally controlled missiles that are employed to defendagainst incoming missiles require pinpoint position accuracy in order tointercept an incoming missile that may be able to change its directionas a defence against the incoming missile.

[0006] Even if defences are actioned early, the size of the target andthe relative approach speed of the defensive missile makes any latecorrection of flight path difficult and limits the chances of defensivemissiles making a direct hit. Directionally controlled missiles may berequired to make rapid changes to their flight paths in order tointercept their target.

[0007] Propelled missiles, such as ground-to-air, sea-to-air,air-to-air, ground-to-sea, air-to-sea, sea-to-sea, air-to-ground,sea-to-ground and ground-to-ground, are also employed to attack targetsthat may make evasive manoeuvers once the incoming threat has beenidentified.

[0008] Additionally, missiles that are propelled from a barrel by thedetonation of a propellant charge may be required to make rapiddirectional changes to ensure that they hit their targets.

SUMMARY OF THE INVENTION

[0009] We have now found a directional control system that may makerapid corrections of flight path to divert a missile.

[0010] Disclosure of the Invention

[0011] According to the present invention there is provided a missileincluding an array of barrel assemblies, each barrel assembly having aplurality of projectiles axially disposed within a barrel, whichprojectiles are associated with discrete propellant charges forpropelling said projectiles sequentially from the barrel, wherein saidarray of barrel assemblies is capable of selectively firing theprojectiles from selected barrels whereby said missile is accelerated bythe reactionary force generated by said firing of projectiles.

[0012] In one embodiment of the invention the missile may be a poweredmissile, such as a rocket or jet powered missile, propelled in acontrolled manner towards its target. Such targets may by stationary orin motion. The present invention is particularly applicable to defensivemissiles targeted onto the converging path of an incoming missile, suchas a high altitude or out-of-atmosphere ballistic missiles. The presentinvention may also be applied to in-atmosphere missiles that mayadvantageously have aerofoils to aid lift in lift and/or stability.

[0013] The present invention is also applicable to missiles that arepropelled from a barrel by the detonation of a propellant charge, suchas high caliber projectiles.

[0014] The present invention may take particular advantage of barrelassemblies of the type described in the present inventor's earlierInternational Patent Application Nos. PCT/AU94/00124 and PCT/AU96/00459.Such barrel assemblies include a barrel, a plurality of projectilesaxially disposed within the barrel for operative sealing engagement withthe bore of the barrel, and discrete propellant charges for propellingrespective projectiles sequentially through the muzzle of the barrel.

[0015] The overall shape of the projectile is not narrowly critical, asthe projectile is a mass against which the propellant acts and exerts areactionary force on the breech of the barrel. In the context of thepresent invention the breech may be formed by subsequent projectilesremaining in the barrel in sealing engagement with the bore of thebarrel. The reactionary force is transferred from the breech of thebarrel to the missile and results in an acceleration of the missile.

[0016] The projectiles may be conventionally shaped, dart-like,generally spherical or any other convenient shape. The projectile mayalso include fins or aerofoils that may advantageously be offset togenerate a stabilising spin, and/or directional lift as the dart ispropelled from a barrel that may be a smooth-bored barrel.

[0017] The projectile is propelled by a charge that may be located in apropellant space and may be formed as a solid block to assist in loadingthe barrel assemblies. Alternatively the propellant charge may beencased and may include an embedded primer having external contact meansadapted for contacting a pre-positioned electrical contact associatedwith the barrel. For example the primer could be provided with a sprungcontact which may be retracted to enable insertion of the cased chargeinto the barrel and to spring out into a barrel aperture upon alignmentwith that aperture for operative contact with its mating barrel contact.If desired the outer case may be consumable or may chemically assist thepropellant burn. Furthermore an assembly of stacked and bonded orseparate cased charges and projectiles may be provided to facilitate thereloading of a barrel.

[0018] The barrel may be non-metallic and the bore of the barrel mayinclude recesses that may fully or partly accommodate the ignitionmeans. In this configuration the barrel may house electrical conductorswhich facilitate electrical communication between the control means andignition means. This configuration may be utilised for disposable barrelassemblies that have a limited firing life and the ignition means andcontrol wire or wires therefor can be integrally manufactured with thebarrel. A barrel assembly may alternatively include ignition aperturesin the barrel and the ignition means are disposed outside the barrel andadjacent the apertures. The barrel may be surrounded by a non-metallicouter barrel which may include recesses adapted to accommodate theignition means. The outer barrel may also house electrical conductorswhich facilitate electrical communication between the control means andignition means. The outer barrel may be formed as a laminated plasticsbarrel which may include a printed circuit laminate for the ignitionmeans.

[0019] The electrical ignition for sequentially igniting the propellantcharges of a barrel assembly may preferably include the steps ofigniting the leading propellant charge by sending an ignition signalthrough the stacked projectiles, and causing ignition of the leadingpropellant charge to arm the next propellant charge for actuation by thenext ignition signal. Suitably all propellant charges inwardly from theend of a loaded barrel are disarmed by the insertion of respectiveinsulating fuses disposed between normally closed electrical contacts.

[0020] Ignition of the propellant may be achieved electrically orignition may utilise conventional firing pin type methods such as byusing a centre-fire primer igniting the outermost projectile andcontrolled consequent ignition causing sequential ignition of thepropellant charge of subsequent rounds. This may be achieved bycalculated reaction and/or controlled rearward leakage of combustiongases or controlled burning of fuse columns extending through theprojectiles or the barrel.

[0021] In another form the ignition is electronically controlled withrespective propellant charges being associated with primers which aretriggered by distinctive ignition signals. For example the primers inthe stacked propellant charges may be sequenced for increasing pulsewidth ignition requirements whereby electronic controls may selectivelysend ignition pulses of increasing pulse widths to ignite the propellantcharges sequentially in a selected time order. Preferably however thepropellant charges are ignited by a set pulse width signal and burningof the leading propellant charge arms the next propellant charge foractuation by the next emitted pulse.

[0022] Suitably in such embodiments all propellant charges inwardly fromthe end of a loaded barrel are disarmed by the insertion of respectiveinsulating fuses disposed between insertion of respective insulatingfuses disposed between normally closed electrical contacts, the fusesbeing set to burn to enable the contacts to close upon transmission of asuitable triggering signal and each insulating fuse being open to arespective leading propellant charge for ignition thereby.

[0023] A number of projectiles can be fired simultaneously from aplurality of barrels or in quick succession from the one barrel. In sucharrangements the electrical signal may be carried externally of thebarrel or it may be carried through the superimposed projectiles whichmay clip on to one another to continue the electrical circuit throughthe barrel, or abut in electrical contact with one another. Theprojectiles may carry the control circuit or they may form a circuitwith the barrel.

[0024] The array of barrel assemblies may be disposed radially from thecenter of mass of the missile. Such configurations are particularlysuited to missiles that do not incorporate a propulsion system. Thefiring of projectiles simply displaces the missile and the missilecontinues upon its trajectory, save for the displacement. Whilstradially disposed arrays of barrel assemblies may also be used toadvantage in missiles incorporating propulsion systems, arrays of barrelassemblies that generate a moment, or turning force, on the missile areparticularly preferred. The rapid turning of the missile by the firingof the projectiles permits the attitude of the missile to be controlledwhilst the missile is being propelled such as by its rocket or jetpropulsion system.

[0025] The array of barrel assemblies may be arranged adjacent theleading end or the trailing end of the missile for effecting changes inattitude of the missile or medially for displacing laterally displacingthe missile. Alternatively the directional control system may include anarray of barrel assemblies adjacent both leading and trailing ends ofthe missile.

[0026] The or each array of barrel assemblies may fire a projectile in adirection having a longitudinal component in order to provide aconsequent addition to the kinetic energy of the missile or a componentin a direction tangential to the longitudinal axis of the missile inorder to impart or change missile rotation about its longitudinal axis.

[0027] The barrel assembly may fire across flight surfaces such as awing to induce a further steering effect to the missile. Alternativelybarrel assemblies may extend through the aerofoil surfaces so as to firein both directions. This may add structural strength to the aerodynamicdesign.

[0028] If desired, a separate array or opposing arrays of barrelassemblies may be provided to control missile rotation about thelongitudinal axis of the missile. The configuration of the arrays mayinclude opposing pairs of barrel assemblies which are firedsimultaneously to effect changes in rotation about the longitudinal axisof the missile only. The projectiles may be selectively actuated beforeand/or after firing projectiles from the directional control system tonegate or utilize the effects on the missile of such rotation about itslongitudinal axis.

[0029] In a preferred embodiment of the invention the directionalcontrol system includes a leading array of barrel assemblies disposedabout the front end of the missile and from each of which a projectilemay be selectively fired in a radial direction relative to thelongitudinal axis of the missile and a trailing array of barrelassemblies about the rear which may be selectively fired in a directionhaving a radial component and a rearward component.

[0030] In certain embodiments of the present invention all the energyrequired to change attitude and the flight direction may be provided bythe firing of projectiles from the barrel assemblies.

[0031] In certain applications a plurality of missiles of the presentinvention may be transported in a housing mounted on a rocket, jet orother transport to be released or fired at a target. For examplemissiles of the present invention may be housed in a directionallycontrolled missile such as that employed to defend against incomingmissiles. Such missiles may themselves incorporate a divert propulsionsystem of the type described in the present application. For conveniencewe will refer to missiles for transporting missiles of the presentinvention as transport missiles although it will be understood that thetransport missiles may themselves impact with the target.

[0032] Incoming high altitude ballistic missiles may carry up to 100warheads, 90% of which may be decoy warheads, and on sensing theapproach of a antimissile missile deploy its payload of warheads makingthe task of destroying the threat many fold more difficult. A transportmissile carrying a multiplicity of missiles of the present invention maydeploy or fire the missiles at the individual warheads. The missiles ofthe present invention may be directionally controlled to impact withtheir targets by a divert propulsion system whereby projectiles arefired from the array of barrel assemblies. The high rates of fire makethis divert propulsion system viable.

[0033] For example a number of missiles may be assigned to each warheadand its direction controlled by an advanced tracking and coordinationsystem on the transport missile that is in communication with a divertpropulsion control on each missile. The divert propulsion control oneach missile may then simply activate the firing of the projectiles ofselected the projectiles to be fired in order to attain the desiredcorrection to trajectory of the missile in response to instructions fromthe advanced tracking and coordination system on the transport missile.

[0034] Advantageously the present invention may also provide adirectional control system, which will maintain or increase the kineticenergy of the missile at impact with the target. The defensive missilehead may advantageously be turned side on just before predicted impactto increase the frontal area, and therefore increasing the killprobability.

[0035] In another aspect this invention resides broadly in a method ofcontrolling the direction of a missile including selectively firing oneor more projectiles from an array of barrel assemblies disposed on saidmissile wherein each barrel assembly of said array of barrel assemblieshaving a plurality of projectiles axially disposed within a barrel,which projectiles are associated with discrete propellant charges forpropelling said projectiles sequentially from the barrel, wherein saidarray of barrel assemblies is capable of selectively firing theprojectiles from selected barrels whereby the direction of said missileis controlled by the reactionary force generated by said firing ofprojectiles.

BRIEF DETAILS OF THE DRAWINGS

[0036] In order that this invention may be more readily understood andput into practical effect reference will now be made to the accompanyingdrawings which illustrate a typical application of this invention,wherein:

[0037]FIG. 1 is a side view of a missile according to one aspect of thisinvention;

[0038]FIG. 2 is a sectional end view through the forward array of barrelassemblies in FIG. 1;

[0039]FIG. 3 is a longitudinal sectional view through the rear array ofbarrel assemblies in FIG. 1, and

[0040]FIG. 4 illustrates the defence of a tank being attacked by amissile.

DESCRIPTION OF EMBODIMENTS OF THE INVENTION

[0041] The rocket powered missile 10 illustrated in FIG. 1 has aplurality of barrel assemblies 11 of the type described arranged aboutthe front end portion 12 and forming a leading array 13 of barrelassemblies and about the tail of the missile forming a trailing array14.

[0042] In the leading array 13, as illustrated in FIG. 2, each barrelassembly 11 is arranged radially off the longitudinal axis 15 of themissile 10, while the barrel assemblies 11 in the trailing array divergerearwardly and outwardly and with their respective barrel axes 16radiating from the axis 15, as illustrated in FIG. 3.

[0043] Each barrel assembly 11 contains one to twelve projectiles 17which may be fired individually, or as a burst, at a selected rate offire up to 500,000 rounds per second (rps). Each projectile fired willcause a reaction in the missile 10 which, if longitudinally displacedfrom the centre of gravity (CG) of the missile 10, will deflect themissile 10 onto a new course. If a projectile is fired from a selectedbarrel assembly 11 a of the leading barrel array 13, the reaction willdeflect the nose portion 12 in the opposite direction A, as illustratedin FIG. 2 and this will result in the missile assuming a new course.

[0044] This action may reduce the total kinetic energy of the missile.However if a projectile is fired from an opposing barrel assembly 11 inthe trailing array 14, not only will the reaction be greater resultingfrom an applied moment, firing from the trailing array will provide aboost the kinetic energy of the missile. This effect can be used toadvantage after all steering corrections have been made, by firing asmany of the remaining projectiles from the trailing array 14 as ispossible just before impact so as to further increase the kinetic energyof the attacking missile. The missile may simply rely on impact or bearmed with a warhead.

[0045] Referring to FIG. 4 it will be seen that the defending missile 10is shown at various positions in its controlled path to collision withan incoming missile 20 attacking a tank 21. The defending missile 10initially may have a path, which would take it above an interceptingposition. Thus at location 24, projectiles are fired upwardly from theleading array 13 and downwardly from the trailing array 14 so as todivert its course downward to location 25 where a further correspondingcorrection is performed.

[0046] At position 26 an opposing correction is performed to elevate thenose of the missile 10 so as to align it to a near head-on course withthe incoming missile 20. Then at the last instant a further nose downcorrection is performed together with any sideways correction to placethe defending missile onto its final collision course with the attackingmissile 20. At that time the remaining rounds in the trailing array 14which may be fired without causing the missile to move out of itscollision path may be fired to increase the kinetic energy of thedefending missile and thus its lethality. At or shortly after impactwith a target any remaining rounds may be fired with a view to causinggreater destruction of the target.

[0047] The defending missile 10 may fly a somewhat zigzag course or aground-hugging course to its target so that it is less vulnerable todetection and/or attack.

[0048] The above has been given only by way of illustrative example ofthis invention and it is to be understood that all such and othermodifications and variations thereto as would be apparent to personsskilled in the art are deemed to fall within the broad scope and ambitof this invention as is herein set forth.

1. A missile including an array of barrel assemblies, each barrelassembly having a plurality of projectiles axially disposed within abarrel, which projectiles are associated with discrete propellantcharges for propelling said projectiles sequentially from the barrel,wherein said array of barrel assemblies is capable of selectively firingthe projectiles from selected barrels whereby said missile isaccelerated by the reactionary force generated by said firing ofprojectiles.
 2. A missile according to claim 1 wherein said missile is apowered missile.
 3. A missile according to claim 2 wherein said poweredmissile includes a rocket or jet propulsion system.
 4. A missileaccording to any one of claims 1 to 3 wherein said missile is selectedfrom the group consisting of high altitude ballistic missiles,out-of-atmosphere ballistic missiles and in-atmosphere missiles.
 5. Amissile according to any one of claims 1 to 4 wherein said array ofbarrel assemblies is disposed radially from the center of mass of themissile.
 6. A missile according to any one of claims 1 to 5 wherein aplurality of arrays of barrel assemblies are radially disposed whereby amoment, or turning force, is created on the missile by the selectivefiring of the projectiles.
 7. A missile according to claim 6 wherein oneof said plurality of arrays of barrel assemblies is arranged adjacenteither the leading end or the trailing end of the missile.
 8. A missileaccording to claim 6 wherein an array of barrel assemblies is arrangedadjacent both leading and trailing ends of the missile.
 9. A missileaccording to any one of claims 1 to 8 wherein said array or arrays ofbarrel assemblies selectively fires projectiles in a direction having acomponent substantially parallel to a longitudinal axis of the missilein order to provide a consequent change to the kinetic energy of themissile.
 10. A missile according to any one of claims 1 to 9 whereinsaid array of barrel assemblies is disposed to control missile rotationabout the longitudinal axis of the missile.
 11. A missile according toclaim 1 wherein said missile is propelled from a barrel by thedetonation of a propellant charge.
 12. A missile according to claim 11wherein said array of barrel assemblies is disposed radially from thecenter of mass of the missile.
 13. A missile according to any one ofclaims 7 to 12 wherein initiation of the propellant charges iselectronically controlled with respective propellant charges beingassociated with primers which are triggered by distinctive ignitionsignals.
 14. A missile according to any one of claims 1 to 13 wherein aselected number of projectiles are fired simultaneously from a pluralityof barrels.
 15. A missile according to any one of claims 1 to 14 whereina selected number of projectiles are fired in quick succession from onebarrel.
 16. A transport missile carrying a multiplicity of missilesaccording to any one of claims 1 to
 15. 17. A transport missileaccording to claim 16 including tracking and coordination systemswhereby the firing of selected projectiles from arrays of barrelassemblies on the missiles are controlled by said tracking andcoordination system.
 18. A method of controlling the direction of amissile, said missile having an array of barrel assemblies disposed onsaid missile, each barrel assembly having a plurality of projectilesaxially disposed within a barrel, which projectiles are associated withdiscrete propellant charges for propelling said projectiles sequentiallyfrom the barrel; said method including selectively firing one or moreprojectiles from the array of barrel assemblies, wherein said array ofbarrel assemblies is capable of selectively firing the projectiles fromselected barrels whereby the direction of said missile is controlled bythe reactionary force generated by said firing of projectiles.